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Engine Design Implications for a Blended Wing-Body Aircraft with Boundary Layer Ingestion

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Engine Design Implications for a Blended Wing-Body Aircraft with Boundary Layer Ingestion Engine Design Implications for a Blended Wing-Body Aircraft with Boundary Layer Ingestion by Christopher J. Hanlon B.S. Aerospace Engineering The Georgia Institute of Technology, 2000 SUBMITTED TO THE DEPARTMENT OF AERONAUTICS AND ASTRONAUTICS IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF MASTER OF ENGINEERING MASSACHUSETTS INSTITUTE AT THE OFTECHNOLOGY MASSACHUSETTS INSTITUTE OF TECHNOLOGY SE P 1 0 2003 F FEBRUARY 2003 -. LIBRARIES C 2003 Christopher J. Hanlon. All Rights Reserved This author hereby grants MIT permission to reproduce an146 distribute publicly paper and electronic copies of this thesis documen i1 whole or in part Signature of Author: Delagafent efAeronautics and Astronautics ->ff 72 Janyary'1", 2003 Certified by: Charles Bo e Senior Lecturer, Department of Aeronautics and Astronadtics Thesis Supervisor Certified by: \ Zoltan S. Spakovszky C.R. Soderberg Assistant Professor of Aeronautics and Astronauti Thesis Supefiisor Accepted by: Edward M. Greitzer H.N. Slater Professor of Aeronautics and Astronautics Chairman, Graduate Office AEqRJ, Engine Design Implications for a Blended Wing-Body Aircraft with Boundary Layer Ingestion by Christopher J. Hanlon Submitted to the Department of Aeronautics and Astronautics on January 17, 2003 in Partial Fulfillment of the Requirements for the Master of Engineering Degree in Aeronautics and Astronautics Abstract Boeing's Blended Wing-Body Commercial Transport (BWB) has evolved over the course of its history with a traditional pylon-pod propulsion system arrangement mounted on the aft end of the centerbody. However, this novel aircraft configuration lends itself well to a more highly integrated propulsion system. It is believed that a more integrated system with boundary layer ingestion (BLI) will promote gains in propulsive efficiency and reductions in overall system complexity, thus reducing the cost of the embedded configuration with respect to the traditional pylon-pod configuration. The closest analogy to this unconventional approach is a torpedo where the hydrodynamic efficiency of the vehicle is dramatically improved by the propeller ingesting the body boundary layer. Given the geometry of the BWB a similar improvement may be possible for this aircraft. Consequently, the goal of this project is to generate a design of a concept that would exploit this effect and then quantify the impact of boundary layer ingestion on the propulsion system design. To this end, a configuration ingesting boundary layer air from the top and bottom surfaces of the centerbody is proposed based on design drivers where the potential benefits of the torpedo effect are maximized. Within this context, a parametric cycle analysis is conducted to quantify the impact of inlet pressure recovery on the performance and design characteristics of the engines. A trade study is conducted to establish the optimum propulsive cycle selection with allowances for system weight and BLI effects. A maximum fuel burn savings of 4.2% is predicted. The inlet distortion level for the concept is quantified along with the associated compression system design implications. One additional high-pressure compressor stage and a 4% fan speed increase are required to maintain adequate surge margin. Additional factors such as engine mechanical design, noise and cost are also considered from a more qualitative standpoint. With this analysis, the design space for an embedded engine becomes developed. and subsequently the design trends from a traditional propulsion system to an embedded one utilizing BLI are generated. 2 Acknowledgements I would first like to thank my thesis advisor, Charles Boppe, for his assistance in producing this thesis. His insight and advice was instrumental in shaping the project scope and direction. Thanks also due to Professor Zoltan Spakovszky for his help in meeting the many technical challenges associated with this project and consequently lending credibility to the analysis. This project was a very complicated endeavor and would not have been successful without the help of these two individuals. Their calm, unassuming nature and precise guidance made working with them a very pleasant and rewarding experience. I am very grateful to my employer, Pratt & Whitney, for the flexibility and support required to meet this goal. Specifically I would like to recognize my supervisor, Jerry Smutney, for his genuine commitment to employee fulfillment. He is an exemplary manger and I am fortunate to have been given the opportunity to work with him and look forward to continued relations in the future. I want to express my appreciation to Boeing for supplying the resources and support necessary to accomplish the project goals. Here I want to thank Dr. Robert Liebeck for lending his time in the evaluation of the project scope, objectives, and results. His involvement added tremendous value to the project. Certainly, the importance of friends and family cannot be overstated. In this regard I feel I have been very fortunate. For providing a welcome departure from the rigors of academia I thank you all. Kelly, thank you for your unwavering patience and good humor. You have, more than anyone else, helped me to realize what is truly important. This thesis is dedicated to my parents, David and Jennifer Hanlon, to which I am very grateful. I have been blessed with parents very dedicated and engaged in the events of their children's lives and attribute my success to them. By instilling values and ethics they made fulfilling this goal a possibility. Dad,I will neverforget the courage andpride you demonstratedin the face of overwhelming circumstances. You left an example by which I would do well to duplicate. Thank you. 3 Table of Contents Abstract....................................................................................................... 2 Table of Contents......................................................................................... 4 Table of Figures .......................................................................................... 6 N om enclature............................................................................................... 7 1. Introduction............................................................................................. 8 1.1 Background: The Blended W ing-Body Concept .............................................. 8 1.2 Embedded Propulsion Systems......................................................................... 9 1.3 Thesis Objectives............................................................................................. 11 2. BLI Physics............................................................................................. 12 2.1 Previous W ork ................................................................................................. 12 2.2 Introduction...................................................................................................... 12 2.3 W ake Analysis of BLI Phenomena.................................................................. 13 2.3.1 Induced Drag W ake ..................................................................................... 14 2.3.2 Viscous Drag W ake ..................................................................................... 16 2.3.3 Propulsion System W ake ................................................................................. 17 2.3.4 BLI from a W ake Analysis Perspective........................................................... 17 2.4 Application to BW B Propulsion System Design................................................ 19 2.5 Thrust-Drag Bookkeeping .............................................................................. 19 3. Concept Generation and Down-Select................................................... 22 3.1 Project Initiation............................................................................................. 22 3.2 Configuration Generation .............................................................................. 25 3.3 Configuration Assessment & Down-select...................................................... 30 3.4 Boeing Feedback............................................................................................. 36 4. Param etric Cycle Analysis...................................................................... 37 4.1 Fundamental Propulsion Theory.................................................................... 37 4.2 Parametric Cycle Results for Turbofan Engines............................................ 42 4.2.1 Engine Specific Thrust and Airflow Demand.................................................. 44 4.2.2 Fan Diameter Sizing ..................................................................................... 45 4.2.3 Overall Efficiency and Specific Fuel Consumption .................................... 47 4.2.4 Gas Generator Core Size Impact.................................................................. 51 4 4.3 Cycle Analysis Summary............................................................................... 52 5. Propulsive Cycle Design........................................................................ 53 5.1 Boundary Layer M odel................................................................................... 55 5.2 Engine Performance........................................................................................ 56 5.3 Engine Inlet Recovery & BLI Drag Reduction Calculation.......................... 57 5.4 BLI W eight Reduction & Trade Factors........................................................
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